Integrity evaluation of aging structures is extremely important to ensure economic and safe operation of the flight vehicle. A two step analytical approach has been developed to estimate the residual strength/life of pressurized fuselage stiffened shell panels with widespread fatigue cracking. Global FEA, to obtain the load flow pattern through the damaged panel, is followed by the Schwartz-Neumann Alternating Method to determine the relevant crack tip parameters that govern the growth of cracks and onset of failure. An Elastic-Plastic Alternativing Method has been developed and applied to evaluate the residual strength of flat panels with multiple cracks. The computational methodologies presented herein are marked improvements to the present state-of-the-art, and are extremely efficient, both from engineering manpower as well as computational costs point of view.


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    Title :

    Structural integrity of panels with multisite fatigue damage


    Additional title:

    Bauliche Unversehrtheit von Platten mit Mehrfachermüdungsschäden


    Contributors:
    Park, J.H. (author) / Singh, R. (author) / Pyo, C.R. (author) / Atluri, S.N. (author)


    Publication date :

    1994


    Size :

    10 Seiten, 11 Bilder, 4 Tabellen, 12 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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